Investigation of behavior of detonation wave in oncoming flowing stoichiometric mixture of hydrogen-oxygen gases was made to study combustion instability in rocket motors and possible application to supersonic combustion; apparatus was designed to measure relative wave velocity and to photograph wave profile as fully developed detonation wave propagated against flow; Mach number of flowing unburned gas was varied from 0.14 to 4; subsonic flow results were in good agreement with Chapman-Jouguet theory; but supersonic flow results indicated strong detonation wave.
Interaction between detonation waves and flowfields
AIAA J
AIAA Journal ; 5 , n 5
1967
6 pages
Article (Journal)
English
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Interaction between detonation waves and flowfields.
AIAA | 1967
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